CA1255123A - Turbine blade superalloy ii - Google Patents
Turbine blade superalloy iiInfo
- Publication number
- CA1255123A CA1255123A CA000503724A CA503724A CA1255123A CA 1255123 A CA1255123 A CA 1255123A CA 000503724 A CA000503724 A CA 000503724A CA 503724 A CA503724 A CA 503724A CA 1255123 A CA1255123 A CA 1255123A
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- alloy
- alloy body
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- molybdenum
- tungsten
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- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C32/00—Non-ferrous alloys containing at least 5% by weight but less than 50% by weight of oxides, carbides, borides, nitrides, silicides or other metal compounds, e.g. oxynitrides, sulfides, whether added as such or formed in situ
- C22C32/001—Non-ferrous alloys containing at least 5% by weight but less than 50% by weight of oxides, carbides, borides, nitrides, silicides or other metal compounds, e.g. oxynitrides, sulfides, whether added as such or formed in situ with only oxides
- C22C32/0015—Non-ferrous alloys containing at least 5% by weight but less than 50% by weight of oxides, carbides, borides, nitrides, silicides or other metal compounds, e.g. oxynitrides, sulfides, whether added as such or formed in situ with only oxides with only single oxides as main non-metallic constituents
- C22C32/0026—Matrix based on Ni, Co, Cr or alloys thereof
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- Engineering & Computer Science (AREA)
- Materials Engineering (AREA)
- Mechanical Engineering (AREA)
- Metallurgy (AREA)
- Organic Chemistry (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Powder Metallurgy (AREA)
- Manufacture And Refinement Of Metals (AREA)
- Chemically Coating (AREA)
Abstract
ABSTRACT
A novel, nickel-base, high temperature alloy body preferably containing about 20% chromium, 6 to 7% aluminum to provied ? phase, 1.5 to 2.5% molybdenum, 3 to 4.5% tungsten, additional strengthening elements and oxidic yttrium in finely dispersed form. The alloy body has an elongated crystal structure and is characterized by high strength along with excellent hot corrosion and oxidation resistance.
A novel, nickel-base, high temperature alloy body preferably containing about 20% chromium, 6 to 7% aluminum to provied ? phase, 1.5 to 2.5% molybdenum, 3 to 4.5% tungsten, additional strengthening elements and oxidic yttrium in finely dispersed form. The alloy body has an elongated crystal structure and is characterized by high strength along with excellent hot corrosion and oxidation resistance.
Description
l PC-5861 TUR~INE RLADE SUPERALLOY II
~ The present invention is dlrected to metallic alloy bodies especiallv suitable for use as structures in hot sections of an industrial ~as turbine (IGT) and more particularly to nickel-base alloy bodtes sultable for such usage.
BACKGRO~ND AND PROBEEM
A modern, advanced desi~n industrial gas turbine (IGT) has hot sta~e blades and vanes which are re~uired to perform for llves of 2 to 5 x 10 up to lO hours, e.~. at least ahout 30,000 hours in a corrodln~
envlronment resu]tln~ from the combustlon of relativelY low Rra~e fuel~
and, in the case of blades, under hlgh stress. Na~urally, in order to increase efficlenc~, lt i8 deslred to operate such IGT blades and vanes at the h~hest pr~ctical operatlng temperatures consistent with achievlng the desi~n life-tlmes. When considering operatln~ temperatures, it is necessary to take into account not onlv the hl~he~t temperature to wh~ch R turbine blade is exposed, but also a ranRe of temperatures below that hl~hes~ temperature. Fven at steadY-state operatlon, a turbine blade wlll experlence a variety of temperatures alon~ its lengtll from root to ~lp and across lt~ width from leadln~ to trailing ed~e.
. :. - ..
.,,., :- . '
~ The present invention is dlrected to metallic alloy bodies especiallv suitable for use as structures in hot sections of an industrial ~as turbine (IGT) and more particularly to nickel-base alloy bodtes sultable for such usage.
BACKGRO~ND AND PROBEEM
A modern, advanced desi~n industrial gas turbine (IGT) has hot sta~e blades and vanes which are re~uired to perform for llves of 2 to 5 x 10 up to lO hours, e.~. at least ahout 30,000 hours in a corrodln~
envlronment resu]tln~ from the combustlon of relativelY low Rra~e fuel~
and, in the case of blades, under hlgh stress. Na~urally, in order to increase efficlenc~, lt i8 deslred to operate such IGT blades and vanes at the h~hest pr~ctical operatlng temperatures consistent with achievlng the desi~n life-tlmes. When considering operatln~ temperatures, it is necessary to take into account not onlv the hl~he~t temperature to wh~ch R turbine blade is exposed, but also a ranRe of temperatures below that hl~hes~ temperature. Fven at steadY-state operatlon, a turbine blade wlll experlence a variety of temperatures alon~ its lengtll from root to ~lp and across lt~ width from leadln~ to trailing ed~e.
. :. - ..
.,,., :- . '
2 PC-5861 Over ~he lon~ de6ign lives of IGT blades and vnnes, corrcsion resl~tance ~nd oxl~ation resl~tance become more lmportant f~ctors than they are ln the well-developed field of alrcraft ~a~ turblne (AGT~
allovs. Althou~h in nelther the c~se of AGT nor IGT turbine blades or vanes would lt be AdvisAble to selec~ sn oxidation or corrosion prone alloy, the longer ~by an order of ma~nitude) time exposure of IGT compo-nents to a more corroding atmosphere make oxldation and eorrosion reslst-ance very import~ne features of IGT alloY structures. IGT alloy structure~ fiUCh as hot sta~e blades and vanes can be coated with conventlonal coatings to enhance oxidation and corrosion resistance but these coatings are fiub~ect to cracklng, spalling and the like. Over the long desl~n llves of IGT components, it ls ~ore likelv that coating failures will occur in compari~on to such failures with AGT coated coTnponents used for shorter time periods. Thus, even if coated, an IGT
alloy structure used in the hot stage of an IGT mus~ have the best oxidation and corrosion resistance obtainable commensurate with other required propertles and characterlstics.
In desi~nin~ alloy structures for IGT turbine blade~ lt is natural to investlgate nickel-base alloys which are used conventionallv ln AGT turbine blades. Even the strongest conventional, y strengthened nicke] base alloys rapidly lose stren~th at temperatures above about 900C (see Fi~ure 2 of U.S. Patent No. 4~386~976)o It ls dlsclosed ln U.S. Patent No. 49386~976 however that nlckel-base alloys co~bining Y
stren~thenlnR and ~trengthenln~ bY a uniform dlspersion of microflne refractorv oxldlc particles can provlde adequate mechanical properties in the temperature ranRe of 750C up to 1100. However, the alloys dl~closed in U.S. Patene No. 4,306,976 are deemed to have inadequate oxldatlon and corroslon reslstance for use ln advsnced deslgn IGTs, It is also known, for example, from U.S. Patent No. 4~039~330 th8t Y
strengthened nickel-ba~e allovs containin~ ln the vlclnlty of 2l to 24 weiRht percent chromium along wlth some aluminum have excellent corrosion and oxldatlon resistance, of the character needed for IGT usage. At very hi~h temperatures, e.g. over 1000C, the oxld~tlon reslstance of allovs as disclo.~ed in U.S. Patent No. 4~039~330 tends to fall off. ~trength at 35 temperatures in excess of gnooc of the allovs dlsclosed ln U.S. Patent No. 4~039~330~ as wlth 811 Y strengthened nickel-base Alloys ls _ inadequate for components of advanced desi~n I~T~.
allovs. Althou~h in nelther the c~se of AGT nor IGT turbine blades or vanes would lt be AdvisAble to selec~ sn oxidation or corrosion prone alloy, the longer ~by an order of ma~nitude) time exposure of IGT compo-nents to a more corroding atmosphere make oxldation and eorrosion reslst-ance very import~ne features of IGT alloY structures. IGT alloy structure~ fiUCh as hot sta~e blades and vanes can be coated with conventlonal coatings to enhance oxidation and corrosion resistance but these coatings are fiub~ect to cracklng, spalling and the like. Over the long desl~n llves of IGT components, it ls ~ore likelv that coating failures will occur in compari~on to such failures with AGT coated coTnponents used for shorter time periods. Thus, even if coated, an IGT
alloy structure used in the hot stage of an IGT mus~ have the best oxidation and corrosion resistance obtainable commensurate with other required propertles and characterlstics.
In desi~nin~ alloy structures for IGT turbine blade~ lt is natural to investlgate nickel-base alloys which are used conventionallv ln AGT turbine blades. Even the strongest conventional, y strengthened nicke] base alloys rapidly lose stren~th at temperatures above about 900C (see Fi~ure 2 of U.S. Patent No. 4~386~976)o It ls dlsclosed ln U.S. Patent No. 49386~976 however that nlckel-base alloys co~bining Y
stren~thenlnR and ~trengthenln~ bY a uniform dlspersion of microflne refractorv oxldlc particles can provlde adequate mechanical properties in the temperature ranRe of 750C up to 1100. However, the alloys dl~closed in U.S. Patene No. 4,306,976 are deemed to have inadequate oxldatlon and corroslon reslstance for use ln advsnced deslgn IGTs, It is also known, for example, from U.S. Patent No. 4~039~330 th8t Y
strengthened nickel-ba~e allovs containin~ ln the vlclnlty of 2l to 24 weiRht percent chromium along wlth some aluminum have excellent corrosion and oxldatlon resistance, of the character needed for IGT usage. At very hi~h temperatures, e.g. over 1000C, the oxld~tlon reslstance of allovs as disclo.~ed in U.S. Patent No. 4~039~330 tends to fall off. ~trength at 35 temperatures in excess of gnooc of the allovs dlsclosed ln U.S. Patent No. 4~039~330~ as wlth 811 Y strengthened nickel-base Alloys ls _ inadequate for components of advanced desi~n I~T~.
3 PC-5861 From the back~round ln the immedlately preceding paragraph one mlght be eempted to declare that the solution to providing turbine blades for ~dvanced design IGTs i~ obvlous. Either increase the chromium and/or alumlnum content of Y and dlsperslon strengthened alloys dl~closed in 5 U.S. Patent No. 4,386>976 or add disperslon strengthenlng to the alloys dl~closed in U.S. Patent No. 4,039,330. These appealing, seemingly.
lo~ical 601utions to the existin~ problem are overly slmplistic.
The flrst possibtlity i.e., increasing the chromlum and/or the aluminum content of a known Y and disperslon stren~thened alloy, has two difficulties. Increasln~ either chromlum or aluminum can tend to make a nickel-base nlloy sigma prone. Increase of chromium dlrectly dilutes the nickel content of the alloy matrix remainlng after y phase precipitation. Increasin~ the aluminum content increases the amount of y phase (Ni3Al-Ti) whlch can form in the nickel-base alloy a~ain dilutlng the m~trix with respect to nickel. Detrimental acicular sigma phase t~nds to form in nickel-base allovs having low nickel matrix contents after intermedlate temperature (e.g., 800C) exposure resultlng in low alloy ductility. Because the exlstence of Y phase is essential to component strength at temperatures Up to about 900C, it is necessary to carefully control allov modlficatlon to avold phase instability over the lon~ tenn usage characterlstlc of IGTs where a minimum acceptable ductility is essential. From another polnt of view, indlscriminate allov modiflcation especially in the realm of increasing aluminum and/or chromlum contents presents a dlfflculty in providlng the component mlcrostructure essentia] to stren~th of dlspersion stren~thened alloys at hl~h temperature. Referrin~ a~ain to U.S. Patent No. 4,386,976 Co]umn 1, llne 58 et seq~, lt 1~ disclosed tha~ ODS ~oxlde dispersion stren~thened) allovs mu~t be capable of developing a coarse, elonRated ~rain structure ln order to obtaln ~ood elevated temperature properties thereln. This coarfie, elongated grain structure is developed by directlona], secondary recrvstalllzation at a temperflture above the y solw s temperature and helow the lnclp~ent melting temperature of the alloY (~ee Column fi, line 58 et fieq. of the U.S. Patent No. 4,386,976) or some ~emperature c~o~e to the lnclpient meltln~ temperature. If Y phase ls not soluttoned, the secondary crystallization will not proceed. If the inciplent meltlng temperature of the alloy ig exceeded the oxlde dl~persion wlll be detrlmentally afEected. For practical productlon, the interval between . .
~S~
lo~ical 601utions to the existin~ problem are overly slmplistic.
The flrst possibtlity i.e., increasing the chromlum and/or the aluminum content of a known Y and disperslon stren~thened alloy, has two difficulties. Increasln~ either chromlum or aluminum can tend to make a nickel-base nlloy sigma prone. Increase of chromium dlrectly dilutes the nickel content of the alloy matrix remainlng after y phase precipitation. Increasin~ the aluminum content increases the amount of y phase (Ni3Al-Ti) whlch can form in the nickel-base alloy a~ain dilutlng the m~trix with respect to nickel. Detrimental acicular sigma phase t~nds to form in nickel-base allovs having low nickel matrix contents after intermedlate temperature (e.g., 800C) exposure resultlng in low alloy ductility. Because the exlstence of Y phase is essential to component strength at temperatures Up to about 900C, it is necessary to carefully control allov modlficatlon to avold phase instability over the lon~ tenn usage characterlstlc of IGTs where a minimum acceptable ductility is essential. From another polnt of view, indlscriminate allov modiflcation especially in the realm of increasing aluminum and/or chromlum contents presents a dlfflculty in providlng the component mlcrostructure essentia] to stren~th of dlspersion stren~thened alloys at hl~h temperature. Referrin~ a~ain to U.S. Patent No. 4,386,976 Co]umn 1, llne 58 et seq~, lt 1~ disclosed tha~ ODS ~oxlde dispersion stren~thened) allovs mu~t be capable of developing a coarse, elonRated ~rain structure ln order to obtaln ~ood elevated temperature properties thereln. This coarfie, elongated grain structure is developed by directlona], secondary recrvstalllzation at a temperflture above the y solw s temperature and helow the lnclp~ent melting temperature of the alloY (~ee Column fi, line 58 et fieq. of the U.S. Patent No. 4,386,976) or some ~emperature c~o~e to the lnclpient meltln~ temperature. If Y phase ls not soluttoned, the secondary crystallization will not proceed. If the inciplent meltlng temperature of the alloy ig exceeded the oxlde dl~persion wlll be detrlmentally afEected. For practical productlon, the interval between . .
~S~
4 PC-586l the Y ~olvus temperature snd the temperature of inclplent meltlng must be at lea6t aboue 10 and, more sdvantageously, At least about 20 in celslus units. Because of the ~omplexity of modern ~ strengthened nlloy compositlons and the complex interactlons among the alloyin~ elements, ther~ is no way of predicting the secondary recrystallizatlon lnterval which is a slne qua non for obtalning the high temperature strength in ODS alloys.
The ~ame difficulty applles to the possible idea of providing o~lde dispersion strengthening to a known, high strength y oxldation and corrosion-reslstant alloy. There ls no wav of predicting whether nor not the theoretical ODS-y strengthened alloy can be made on a commercial basis.
The foregoinR makes lt clear ehat the provision of alloy components suitable for hot stage advanced design IGT usage is a problem that requires critical metallurgical balancing to at least provlde an adequate window for thermal treatment necessary for practical production of such components. In addition, the alloy composition must be capable of undergoing the practlcal mechanical and thermomechanical processing required to reach the stage of directional recrystallization.
The present invention provides alloy bodles suitable for use in advance design IGTs which can be produced in a practical manner.
BRI~F DESCRIPTION OF THE DRAWING
The figure is a photograph showing the grain ~tructure of an allov bodv of the invention.
SUMMARY O~ THE INVENTInN
The present invention comtemplates an alloy bodv especiallv useful as a component in hot stages of lndustrial ~as turbines having improved resistance to lon~ term stress at temperatures in the range 800 to 11()~C combined with enhanced o~idation and corrosion resistance. The a]]ov body compri~es at le~st in part, an aggregation of elongated, essentially parallel metallic crystals having graln boundaries there-between wherein the average grain aspect ratlo of said ~etallic crystals is at least about 7. These metallic crystals (1) have a Y phase dl~persed therein ~e a tempera~ure lower than about 1180C and (2) have dispersed therethrough particles in the Rlze range of about 5 to 500 nanometers ln malor d-lmension of an oxidlc phase fftable at temperatures below at least 1100C. The metallic crystal incluslve of dl~persed materlal and grai~ boundary materlal cons~sts essentlally in welght percent of about 18 to 25~ chro~ium, about 5.5 to 9~ aluminum~ up to, i.e. 0 to about 1Z titanium wlth the provlso that the sum of the percentages of aluminum and tltanium is no greater than 9, up to about 4.5Z molYbdenum, about 3 to ~% tungsten, up to about 0.05%, e.~. about 0.005 to 0.05Z boron, up to about 0~5X zlrconlum, about 0.4 to lZ
yttrlum, about 0.4 to about 1~ oxygen, up to about 0.2% carbon, up to about 1~ or 2~ iron, up to about 0.3 or 0.5% nitrogen, up to about 4%
tantalum, up to about 2~ nioblum (~ith the provlso that tantalum, if any, and niobium, if any~ are present in the alloy only when the aluminum content ls below about 7Z), up to about 10% cobalt, up to about 2 hafniu~, up to about 4~ rhenium (in replacement of all or part of molybdenum and/or tungsten) the balance except for impurities and ~ncidental elements being nickel. In these alloy bodies, substantially a~l of the yttrium and a part of the aluminum exist as oxides formlng the princlpal part of the dlspersed stable oxidic phase. Depending upon the exact conditions of manufacture and use, the dispersed oxidic phase can comprise ~ttria and alumina or alumina ~ yttria mixed oxides such as 2 3 ~ 3 2 3 . 23 or 5Al203 . 3Y203 and comprises about 2 5 to about 4 volume percent of the metallic crystals.
Generally speakingg the alloy bodv of the present invention is produced bv mechanically alloving powdered elemental or master allov constituents a]on~ with oxidic yttrium in an attritor or a horizontal ball mil] until substantial saturation hardness 1s obtalned along with thorough lnterworkln~ of thc attrlted metals one wlthin another and effectlve inclusion of the oxide containlng yttrlum withln attrited allov partlcles to provide homo~eneitY. For best results, the milling charge should include powder of an omnibus master allo~, l.e. an alloy contalning all non-oxide alloying ingredien~s in proper proportlon except being poor in nickel or nickel and cobalt. This omnibus ma~ster allov powder is produced bv melting and atomization, e.g. gas atomlzation. The mill charge consists of the omnibus master alloy9 yttria or oxidic _, yttrium nnd approprlate amounts of nlckel, nlckel and cobalt or nickel-cobalt alloy powder.
The mllled powder ls then screened, blended and packed into mlld steel ~xtrusion cans which ~re sealed and may be evacuated. The sealed cans ~re ehen heated to about 1000C to 1200C and hot extruded at an exeruslon ratio of at lesst about 5 using a relatively high strain rate.
After extrusion or equlvalent hot compactlon, the thus processed mechanlcally alloyed material can be hot worked, especlally dlrectionally hot worked by rollln~ or the llke. Thls hot working should be carrled out rapldly In order to preserYe ln the r~etal a slRnlficant fraction of the straln energy induced bY the initlal extrusion or other hot compaction. Once thls ls done, the alloy body of the invention is processed by any suitable means, e.~., zone annealing, to provide coarse elongated ~rains in the body ha~ln~ an average grain aspect ratio (GAR) O~ at-least 7. If required, the thus produced allcy body can be given a solution treatment and a subsequent aglng heat treatment to precipitate Y
phase ln addition to that amount of Y phase forminR on cooling rom grain coarsening temperatures. It has been found that for alloys having a composition within the range as disclosed hereinbefore, the overall graln coarsening interval, l.e., T~ (Temperature of incipient melting) -T , (y' solvus temperatnre) is at least about 20 in Celsius units thereby providlng an adequate processing window for cornmercial production of alloy bodles having coarse elon~ated grains of high GAR. For alloy bodies of the present invention, solution treatment can be for 1 to 20 hours at 1050 to 1300C. Satisf~ctorv a~ing treatments lnvolve holdlng the allov body at a temperature in the ran~e of 600 to 950C for l to 24 hours. An interrnedlate aginR comprlslng holding the alloy body for l to 16 hours in the rar-Re of 800 to l150C lnterposed hetween the solution trestment and the final aRing treatment can be advancaReous.
DESCRTPTION OF THE PREFERRED F,MBODIMENT
Alloy bodies of the present invention advanta~eous]y contain, in combination or singly, the followin~ preferred amounts of allo~in~
ingredients:
~5~
7 PC-5u61 Ingredient Z by Wt. Ingredlent Z by Wt~
.
Cr 19 -21 Co 0 Al 6 - 7 Hf 0 Tl 0 C 0 -0.1 S Ta 0 Re 0 Nb O Zr 0.05-0.25 Mo 1.5- 2.5 U 3 - 4.5 The compositlona, ln ~elght percent, of lngredients analyzed (assumin~ all yttrium to be pre~ent as yttrla), of speciflc examples of allov~ maklng up alloy bodles of the present invention are set forth ln Table I.
TABLE I
Alloy Ni Cr Al Mo W C B Zr 2 3 Fe 0 N
~ _ _ _ _ _ _ _ 15 1 ~al 19.5 6.7 2.0 3.8 0.044 0.011 0.15 O.S7 0.78 0.48 0.16 2-Bal 19.6 6.6 1.9 3.5 0.042 0.011 0.15 0.55 0.80 0.46 0.15 3 ~al 20.2 6.7 2.0 3.5 0.043 0.011 0.16 0.99 0.64 0.52 0.18 Each of the alloy composltlons was prepared by mechanical alloylng of batches ln an attrltor using as raw material nlckel powder Type 123, elemental chromlum, tungsten, molybdenum, tantalum and nioblum, nickel 47.5Z Al master alloy, nlckel-28% zirconium master alloy, nickel-16.9~ boron master alloy and yttria. In each case the powder was processed to homogeneity. Each powder batch was ficreened to remove particles exceedlng 12 mesh, cone blended two hours and packed in~o mlld steel extruslon cans whlch were evacuated and sealed. Up to four extrusion cans were prepared for each compositlon. The cans were heated in the range (1000C to 1200C) and extruded lnto bar at an extruslon ratlo of about 7. Extrusion was performed on 750 ton press at about 35%
throttle setting. The extruded bar material was sub~ected to hot rolling at temperatures from about 12nOC to about 1300C and at total reductlons up to a~out 60Z (pass reductions of about 20%) with no difficu]tles belng encountered.
Heat treating experiments determined that tne extruded bar material would grow a coarse elongated grain flnd that zone annealln~ at an elevated temperature, in the range of about 1200C to about 1315C was an effectlve grain coarsening procedure.
,; .
Tenslle test~, stress-rupture tests, oxidatlon tests and sulfldation te~ts were conduct~d on alloy bodies havln~ a coarse graln structure of high GAR in accordance with the lnvention with the result6 shown in the followin~ Tables. The tensile and stre~s-rupture te6ts were all conducted in the longitudinal direction a8 determined by the ~rain strueeure of the alloy body. Prior to testin~, the alloYs as set forth ~n Table I were formed lnto alloy bodies of the lnvention bY the zone anne~ling treatment set forth in Table II. Particular heat treatments employed are also set forth in Table II.
TABLE II
Zone Anneal Heat Treatment Alloy Temp (C) ~ hours - C - AC (air coolinR) _ .
1 1260 76 2-1279-AC + 2 - 954-AC + 24 - 843-AC
2 1260 76 2-1279-AC ~ 2 ~ 954-AC + 24 - 843-AC
3 1260 76 2-1279-AC ~ 2 - 954-AC + 24 - 843-AC
Some of the alloy bodies of the invention as zone annealed and heat treated as set forth ln Table II were tensile tested at various te~peratures as reported in Table TII.
TABLE III
Y.S. (MLPa) U.T.S. El R . A .
Alloy Body 0.2% Offset (MPa) (%) (%) -ROOM TEMPERATURE
1 1113 1320 3.0 2.5 2 1123 1208 1.0 5.0 1 1013 1237 5.0 4.n 2 1005 1241 5.0 R.5 1 758 876 5.0 fl.5 2 743 916 1.0 1.0 ] 000 C
1 ~24 266 8.0 If~.O
2 207 266 7.0 13.5 9 PC-5~61 TABLE III (CONT'D ) Y.S. (MPa) U.T.S. El R.A.
Alloy 9Ody 0 2% Offset (MPa) (%~ (Z) 1 109 117 17.0 40.0 2 ~16 119 14.0 37.0 Samples of Alloy body 1 eested under stress for creep-rupture exhlblted the characterlstics a~ reported ln Table IV.
TABLE IV
Mlnimum Temperature StressLife EL RA Creep Rate ~C) (MPa)(h) (Z) (Z) (~/h) 816 600 1.1 3.0 ~.0 816 450 16.5 4.0 4.7 816 400111.9 2.5 4.0 - 816 350374.3 1.6 6.7 0.002 816 325714.5 1.5 3.5 816 3001750.6 2.5 2.5 0.00027 816 2704301.8 1.5 2.0 0.00015 982 lg3 2.1 11.2 28.5 982 172 5.7 9.5 ~4.5 982 160 49.7 3.2 9.3 0.0088 982 150 66.7 2.5 1.0 0.0065 982 1352533.3 1.0 2.0 ~.00006 Other tes~s have established the rupture stress capabilities of allov hodies 2 and 3 as set forth in Table V.
TABLE V
Rupture Stress Cap~bllities (MPa~
816C $ 982C
30Alloy Body No. 102h 103h 10 h 102h 103h 10~h 2 375290 240* 160 NA NA
3 410325 260* 160 150 135*
*Extrapolated Value NA - Not Available Yet Alloy body No. 1 was tested for hot corrosion under test conditions (1) at 926C and 843C - JP-5 fuel + 0.3 Wt. ~ S, 5 ppm sea salt, 30:1 alr-eo-fuel ratio, 1 cycle/hour (5~ min. in flame, 2 min. out in air) 500h test duraelon and (2) at 704C - Dlesel ~2 fuel + 3.0 Wt. Z S, 10 .._ .~ 3 ppm sea salt, 3n-1 alr-to-fuel ratio, 1 cycleldny (1425 mlnutes in flame, 15 mi11utes out in ~ir~ 500 hour test duration. At 926C metal los~ was 0.0051 mm with a maxlmum attack of 0.086 mm. At 843C metal ~etal 108s nnd maximum attack were hoth 0.0051 ~m. At 704C metal loss and maxlmum ~ttack were both 0.084 mm.
In addltion to the hot corrosion tests specified in the foregoing para~raph alloy bodies of the lnvention were subJected to cyclic oxidation tests in which alloy body specimens were held at the temperatures speclfied in Table VI in air contalnlng 5% water for 24 hour cycles and then cooled in air for the remainder of the cycle. Table VI
reports results in terms of descaled weight change (mg/cm2) of these tests.
TABLE VI
Descaled Wt. Change (mg/cmZ) AlloY Bodv 1000C/41 Cvcles 1100C/21 C~cles -1 -0.475 -0.928 2 -0.800 -0.992 3 -0.787 -0.916 In order to assess the stability of alloy bodies of the inventlon, they were exposed, unstressed, to an air atmosphere at 81fiC
for various tlmes and then examined, either microscopically or by means of a room temperature tensile test. Microscopic examination of alloy bodies 1 and 3 showed no evidence of formation of sigma phase after 6272 hours of exposure. Room temperature tensile test results of alloy bodies of the present invention after specified times of unstressed exposure at 81hC ln an air atmosphere are set forth in Table VII.
TABLE VII
Exposure Alloy Rody at 816C YS (MPa) UTS ~1. RA. Hardness No. (Hours) 2~ Offset (MPa) ~ ~ (R ) 1 6000 923 1096 4.3 ll,h41-42 1 800n 893 1061 5.1 4.3 43 2 6000 885 1032 3.0 6.2 41 2 8000 872 1050 1.3 3.5 40-41 3 6000 913 1051 1.6 3.3 40-43 Tables III through VII together in comparison ~o data in U.S.
Patent Nos. 4,3869976 and 4,039,330 mentioned hereinbefore show that 1~5 ~
ll PC-5861 alloy bodle~ of the present invention are suitable for use as IGT hot sta~e blRdes and other components. For example, Tables III to V show that in stren~th characteristics, the alloy bodles of the present lnventlon parallel the strength characteristlcs of INCONEL MA6000 (U.S.
Patent No. 3,926,568) whereafi Tables VI and VII show that in corroslon and oxidatlon resistance, the alloy bodles of the present invention exhlbit characterlstics akln to or better than IN-939 (U.S. Patent ~o.
4,039,330). The drawlng depicts the coarse elongated grain structure of the alloy bodies of the inventlon whlch is instrumental ln provldin~
ehelr advanta~eous strength characterlstic6. Referrlng now thereto, the optical photo~raph of the Figure shows the etched o~tline of coarse metallic ~ralns bound together by grain boundary material.
Those skllled in the art will appreclate that alloy bodies of the present invention can include volumes in ~hich the grain structure can deviate from the coarse elon~ated structure depicted in the drawing provided that such volumes are not requlred to possess extreme mechanical characteristics at very high temperatures. For example, in a turbine blade structure, part or all of the root portion can have a ~rain structure differin~ from the coarfie, elon~ated, lon~itudinall~ oriented ~rain structure of the blade portion.
In view of the total aluminum and chromium contents of the alloy bodie~ of the invention, it is expected that these alloY bodies will constitute compatible substrates for both diffused aluminide coatin~s and for various high aluminum, hi~h chromium deposited coatln~s, e.~
M-Cr-Al-Y coatin~s where M is a metallic element such as nickel or coha]t. By use of such coatin~s the already hi~h corrosion and oxidation resistance of alloy bodies of the invention can be further enhanced.
While the present invention has been described with respect to speciflc embodiments, those skilled in the art will appreclate that alterations and modificatlons within the spirit of the lnventlon can be made. Such alterations and modifications are intended to be withln the ambit of the appended clalms.
The ~ame difficulty applles to the possible idea of providing o~lde dispersion strengthening to a known, high strength y oxldation and corrosion-reslstant alloy. There ls no wav of predicting whether nor not the theoretical ODS-y strengthened alloy can be made on a commercial basis.
The foregoinR makes lt clear ehat the provision of alloy components suitable for hot stage advanced design IGT usage is a problem that requires critical metallurgical balancing to at least provlde an adequate window for thermal treatment necessary for practical production of such components. In addition, the alloy composition must be capable of undergoing the practlcal mechanical and thermomechanical processing required to reach the stage of directional recrystallization.
The present invention provides alloy bodles suitable for use in advance design IGTs which can be produced in a practical manner.
BRI~F DESCRIPTION OF THE DRAWING
The figure is a photograph showing the grain ~tructure of an allov bodv of the invention.
SUMMARY O~ THE INVENTInN
The present invention comtemplates an alloy bodv especiallv useful as a component in hot stages of lndustrial ~as turbines having improved resistance to lon~ term stress at temperatures in the range 800 to 11()~C combined with enhanced o~idation and corrosion resistance. The a]]ov body compri~es at le~st in part, an aggregation of elongated, essentially parallel metallic crystals having graln boundaries there-between wherein the average grain aspect ratlo of said ~etallic crystals is at least about 7. These metallic crystals (1) have a Y phase dl~persed therein ~e a tempera~ure lower than about 1180C and (2) have dispersed therethrough particles in the Rlze range of about 5 to 500 nanometers ln malor d-lmension of an oxidlc phase fftable at temperatures below at least 1100C. The metallic crystal incluslve of dl~persed materlal and grai~ boundary materlal cons~sts essentlally in welght percent of about 18 to 25~ chro~ium, about 5.5 to 9~ aluminum~ up to, i.e. 0 to about 1Z titanium wlth the provlso that the sum of the percentages of aluminum and tltanium is no greater than 9, up to about 4.5Z molYbdenum, about 3 to ~% tungsten, up to about 0.05%, e.~. about 0.005 to 0.05Z boron, up to about 0~5X zlrconlum, about 0.4 to lZ
yttrlum, about 0.4 to about 1~ oxygen, up to about 0.2% carbon, up to about 1~ or 2~ iron, up to about 0.3 or 0.5% nitrogen, up to about 4%
tantalum, up to about 2~ nioblum (~ith the provlso that tantalum, if any, and niobium, if any~ are present in the alloy only when the aluminum content ls below about 7Z), up to about 10% cobalt, up to about 2 hafniu~, up to about 4~ rhenium (in replacement of all or part of molybdenum and/or tungsten) the balance except for impurities and ~ncidental elements being nickel. In these alloy bodies, substantially a~l of the yttrium and a part of the aluminum exist as oxides formlng the princlpal part of the dlspersed stable oxidic phase. Depending upon the exact conditions of manufacture and use, the dispersed oxidic phase can comprise ~ttria and alumina or alumina ~ yttria mixed oxides such as 2 3 ~ 3 2 3 . 23 or 5Al203 . 3Y203 and comprises about 2 5 to about 4 volume percent of the metallic crystals.
Generally speakingg the alloy bodv of the present invention is produced bv mechanically alloving powdered elemental or master allov constituents a]on~ with oxidic yttrium in an attritor or a horizontal ball mil] until substantial saturation hardness 1s obtalned along with thorough lnterworkln~ of thc attrlted metals one wlthin another and effectlve inclusion of the oxide containlng yttrlum withln attrited allov partlcles to provide homo~eneitY. For best results, the milling charge should include powder of an omnibus master allo~, l.e. an alloy contalning all non-oxide alloying ingredien~s in proper proportlon except being poor in nickel or nickel and cobalt. This omnibus ma~ster allov powder is produced bv melting and atomization, e.g. gas atomlzation. The mill charge consists of the omnibus master alloy9 yttria or oxidic _, yttrium nnd approprlate amounts of nlckel, nlckel and cobalt or nickel-cobalt alloy powder.
The mllled powder ls then screened, blended and packed into mlld steel ~xtrusion cans which ~re sealed and may be evacuated. The sealed cans ~re ehen heated to about 1000C to 1200C and hot extruded at an exeruslon ratio of at lesst about 5 using a relatively high strain rate.
After extrusion or equlvalent hot compactlon, the thus processed mechanlcally alloyed material can be hot worked, especlally dlrectionally hot worked by rollln~ or the llke. Thls hot working should be carrled out rapldly In order to preserYe ln the r~etal a slRnlficant fraction of the straln energy induced bY the initlal extrusion or other hot compaction. Once thls ls done, the alloy body of the invention is processed by any suitable means, e.~., zone annealing, to provide coarse elongated ~rains in the body ha~ln~ an average grain aspect ratio (GAR) O~ at-least 7. If required, the thus produced allcy body can be given a solution treatment and a subsequent aglng heat treatment to precipitate Y
phase ln addition to that amount of Y phase forminR on cooling rom grain coarsening temperatures. It has been found that for alloys having a composition within the range as disclosed hereinbefore, the overall graln coarsening interval, l.e., T~ (Temperature of incipient melting) -T , (y' solvus temperatnre) is at least about 20 in Celsius units thereby providlng an adequate processing window for cornmercial production of alloy bodles having coarse elon~ated grains of high GAR. For alloy bodies of the present invention, solution treatment can be for 1 to 20 hours at 1050 to 1300C. Satisf~ctorv a~ing treatments lnvolve holdlng the allov body at a temperature in the ran~e of 600 to 950C for l to 24 hours. An interrnedlate aginR comprlslng holding the alloy body for l to 16 hours in the rar-Re of 800 to l150C lnterposed hetween the solution trestment and the final aRing treatment can be advancaReous.
DESCRTPTION OF THE PREFERRED F,MBODIMENT
Alloy bodies of the present invention advanta~eous]y contain, in combination or singly, the followin~ preferred amounts of allo~in~
ingredients:
~5~
7 PC-5u61 Ingredient Z by Wt. Ingredlent Z by Wt~
.
Cr 19 -21 Co 0 Al 6 - 7 Hf 0 Tl 0 C 0 -0.1 S Ta 0 Re 0 Nb O Zr 0.05-0.25 Mo 1.5- 2.5 U 3 - 4.5 The compositlona, ln ~elght percent, of lngredients analyzed (assumin~ all yttrium to be pre~ent as yttrla), of speciflc examples of allov~ maklng up alloy bodles of the present invention are set forth ln Table I.
TABLE I
Alloy Ni Cr Al Mo W C B Zr 2 3 Fe 0 N
~ _ _ _ _ _ _ _ 15 1 ~al 19.5 6.7 2.0 3.8 0.044 0.011 0.15 O.S7 0.78 0.48 0.16 2-Bal 19.6 6.6 1.9 3.5 0.042 0.011 0.15 0.55 0.80 0.46 0.15 3 ~al 20.2 6.7 2.0 3.5 0.043 0.011 0.16 0.99 0.64 0.52 0.18 Each of the alloy composltlons was prepared by mechanical alloylng of batches ln an attrltor using as raw material nlckel powder Type 123, elemental chromlum, tungsten, molybdenum, tantalum and nioblum, nickel 47.5Z Al master alloy, nlckel-28% zirconium master alloy, nickel-16.9~ boron master alloy and yttria. In each case the powder was processed to homogeneity. Each powder batch was ficreened to remove particles exceedlng 12 mesh, cone blended two hours and packed in~o mlld steel extruslon cans whlch were evacuated and sealed. Up to four extrusion cans were prepared for each compositlon. The cans were heated in the range (1000C to 1200C) and extruded lnto bar at an extruslon ratlo of about 7. Extrusion was performed on 750 ton press at about 35%
throttle setting. The extruded bar material was sub~ected to hot rolling at temperatures from about 12nOC to about 1300C and at total reductlons up to a~out 60Z (pass reductions of about 20%) with no difficu]tles belng encountered.
Heat treating experiments determined that tne extruded bar material would grow a coarse elongated grain flnd that zone annealln~ at an elevated temperature, in the range of about 1200C to about 1315C was an effectlve grain coarsening procedure.
,; .
Tenslle test~, stress-rupture tests, oxidatlon tests and sulfldation te~ts were conduct~d on alloy bodies havln~ a coarse graln structure of high GAR in accordance with the lnvention with the result6 shown in the followin~ Tables. The tensile and stre~s-rupture te6ts were all conducted in the longitudinal direction a8 determined by the ~rain strueeure of the alloy body. Prior to testin~, the alloYs as set forth ~n Table I were formed lnto alloy bodies of the lnvention bY the zone anne~ling treatment set forth in Table II. Particular heat treatments employed are also set forth in Table II.
TABLE II
Zone Anneal Heat Treatment Alloy Temp (C) ~ hours - C - AC (air coolinR) _ .
1 1260 76 2-1279-AC + 2 - 954-AC + 24 - 843-AC
2 1260 76 2-1279-AC ~ 2 ~ 954-AC + 24 - 843-AC
3 1260 76 2-1279-AC ~ 2 - 954-AC + 24 - 843-AC
Some of the alloy bodies of the invention as zone annealed and heat treated as set forth ln Table II were tensile tested at various te~peratures as reported in Table TII.
TABLE III
Y.S. (MLPa) U.T.S. El R . A .
Alloy Body 0.2% Offset (MPa) (%) (%) -ROOM TEMPERATURE
1 1113 1320 3.0 2.5 2 1123 1208 1.0 5.0 1 1013 1237 5.0 4.n 2 1005 1241 5.0 R.5 1 758 876 5.0 fl.5 2 743 916 1.0 1.0 ] 000 C
1 ~24 266 8.0 If~.O
2 207 266 7.0 13.5 9 PC-5~61 TABLE III (CONT'D ) Y.S. (MPa) U.T.S. El R.A.
Alloy 9Ody 0 2% Offset (MPa) (%~ (Z) 1 109 117 17.0 40.0 2 ~16 119 14.0 37.0 Samples of Alloy body 1 eested under stress for creep-rupture exhlblted the characterlstics a~ reported ln Table IV.
TABLE IV
Mlnimum Temperature StressLife EL RA Creep Rate ~C) (MPa)(h) (Z) (Z) (~/h) 816 600 1.1 3.0 ~.0 816 450 16.5 4.0 4.7 816 400111.9 2.5 4.0 - 816 350374.3 1.6 6.7 0.002 816 325714.5 1.5 3.5 816 3001750.6 2.5 2.5 0.00027 816 2704301.8 1.5 2.0 0.00015 982 lg3 2.1 11.2 28.5 982 172 5.7 9.5 ~4.5 982 160 49.7 3.2 9.3 0.0088 982 150 66.7 2.5 1.0 0.0065 982 1352533.3 1.0 2.0 ~.00006 Other tes~s have established the rupture stress capabilities of allov hodies 2 and 3 as set forth in Table V.
TABLE V
Rupture Stress Cap~bllities (MPa~
816C $ 982C
30Alloy Body No. 102h 103h 10 h 102h 103h 10~h 2 375290 240* 160 NA NA
3 410325 260* 160 150 135*
*Extrapolated Value NA - Not Available Yet Alloy body No. 1 was tested for hot corrosion under test conditions (1) at 926C and 843C - JP-5 fuel + 0.3 Wt. ~ S, 5 ppm sea salt, 30:1 alr-eo-fuel ratio, 1 cycle/hour (5~ min. in flame, 2 min. out in air) 500h test duraelon and (2) at 704C - Dlesel ~2 fuel + 3.0 Wt. Z S, 10 .._ .~ 3 ppm sea salt, 3n-1 alr-to-fuel ratio, 1 cycleldny (1425 mlnutes in flame, 15 mi11utes out in ~ir~ 500 hour test duration. At 926C metal los~ was 0.0051 mm with a maxlmum attack of 0.086 mm. At 843C metal ~etal 108s nnd maximum attack were hoth 0.0051 ~m. At 704C metal loss and maxlmum ~ttack were both 0.084 mm.
In addltion to the hot corrosion tests specified in the foregoing para~raph alloy bodies of the lnvention were subJected to cyclic oxidation tests in which alloy body specimens were held at the temperatures speclfied in Table VI in air contalnlng 5% water for 24 hour cycles and then cooled in air for the remainder of the cycle. Table VI
reports results in terms of descaled weight change (mg/cm2) of these tests.
TABLE VI
Descaled Wt. Change (mg/cmZ) AlloY Bodv 1000C/41 Cvcles 1100C/21 C~cles -1 -0.475 -0.928 2 -0.800 -0.992 3 -0.787 -0.916 In order to assess the stability of alloy bodies of the inventlon, they were exposed, unstressed, to an air atmosphere at 81fiC
for various tlmes and then examined, either microscopically or by means of a room temperature tensile test. Microscopic examination of alloy bodies 1 and 3 showed no evidence of formation of sigma phase after 6272 hours of exposure. Room temperature tensile test results of alloy bodies of the present invention after specified times of unstressed exposure at 81hC ln an air atmosphere are set forth in Table VII.
TABLE VII
Exposure Alloy Rody at 816C YS (MPa) UTS ~1. RA. Hardness No. (Hours) 2~ Offset (MPa) ~ ~ (R ) 1 6000 923 1096 4.3 ll,h41-42 1 800n 893 1061 5.1 4.3 43 2 6000 885 1032 3.0 6.2 41 2 8000 872 1050 1.3 3.5 40-41 3 6000 913 1051 1.6 3.3 40-43 Tables III through VII together in comparison ~o data in U.S.
Patent Nos. 4,3869976 and 4,039,330 mentioned hereinbefore show that 1~5 ~
ll PC-5861 alloy bodle~ of the present invention are suitable for use as IGT hot sta~e blRdes and other components. For example, Tables III to V show that in stren~th characteristics, the alloy bodles of the present lnventlon parallel the strength characteristlcs of INCONEL MA6000 (U.S.
Patent No. 3,926,568) whereafi Tables VI and VII show that in corroslon and oxidatlon resistance, the alloy bodles of the present invention exhlbit characterlstics akln to or better than IN-939 (U.S. Patent ~o.
4,039,330). The drawlng depicts the coarse elongated grain structure of the alloy bodies of the inventlon whlch is instrumental ln provldin~
ehelr advanta~eous strength characterlstic6. Referrlng now thereto, the optical photo~raph of the Figure shows the etched o~tline of coarse metallic ~ralns bound together by grain boundary material.
Those skllled in the art will appreclate that alloy bodies of the present invention can include volumes in ~hich the grain structure can deviate from the coarse elon~ated structure depicted in the drawing provided that such volumes are not requlred to possess extreme mechanical characteristics at very high temperatures. For example, in a turbine blade structure, part or all of the root portion can have a ~rain structure differin~ from the coarfie, elon~ated, lon~itudinall~ oriented ~rain structure of the blade portion.
In view of the total aluminum and chromium contents of the alloy bodie~ of the invention, it is expected that these alloY bodies will constitute compatible substrates for both diffused aluminide coatin~s and for various high aluminum, hi~h chromium deposited coatln~s, e.~
M-Cr-Al-Y coatin~s where M is a metallic element such as nickel or coha]t. By use of such coatin~s the already hi~h corrosion and oxidation resistance of alloy bodies of the invention can be further enhanced.
While the present invention has been described with respect to speciflc embodiments, those skilled in the art will appreclate that alterations and modificatlons within the spirit of the lnventlon can be made. Such alterations and modifications are intended to be withln the ambit of the appended clalms.
Claims (6)
1. An alloy body especially useful in hot stages of industrial gas turbines having improved resistance to long term stress at temperatures in the range 800° to 1100°C combined with enhanced oxidation and corrosion resistance comprising, in at least part, an aggregation of elongated, essentially parallel metallic crystals having grain boundaries therebetween wherein the average grain aspect ratio of said metallic crystals is at least about 7, said metallic crystals (1) having a .gamma.
phase dispersed therein at a temperature lower than about 1180°C and (2) having dispersed therethrough particles in the range of about 5 to 500 nanometers in major dimension of a stable yttrium-containing oxidic phase, said metallic crystals and grain boundary material consisting essentially in weight percent of about 1% to about 25% chromium, about 5.5 to about 9% aluminum, up to about 1% titanium with the proviso that the amount of the titanium, if any, and the aluminum is no greater than 9%, up to about 4% tantalum, up to about 2% niobium with the proviso that tantalum, if any, and niobium, if any, are present only when the aluminum content is less than about 7%, up to about 4.5% molybdenum, about 3 to about 8% tungsten, up to about 10% cobalt, up to about 2% hafnium, about 0.4 to about 1% oxygen, about 0.4 to about 1% yttrium, up to about 0.2%
carbon, up to about 0.05% boron, up to about 0.5% zirconium, up to about 2% iron, up to about 0.5% nitrogen, up to about 4% rhenium in replacement of an equal percentage of molybdenum or tungsten, the balance, except for impurities being essentially nickel.
phase dispersed therein at a temperature lower than about 1180°C and (2) having dispersed therethrough particles in the range of about 5 to 500 nanometers in major dimension of a stable yttrium-containing oxidic phase, said metallic crystals and grain boundary material consisting essentially in weight percent of about 1% to about 25% chromium, about 5.5 to about 9% aluminum, up to about 1% titanium with the proviso that the amount of the titanium, if any, and the aluminum is no greater than 9%, up to about 4% tantalum, up to about 2% niobium with the proviso that tantalum, if any, and niobium, if any, are present only when the aluminum content is less than about 7%, up to about 4.5% molybdenum, about 3 to about 8% tungsten, up to about 10% cobalt, up to about 2% hafnium, about 0.4 to about 1% oxygen, about 0.4 to about 1% yttrium, up to about 0.2%
carbon, up to about 0.05% boron, up to about 0.5% zirconium, up to about 2% iron, up to about 0.5% nitrogen, up to about 4% rhenium in replacement of an equal percentage of molybdenum or tungsten, the balance, except for impurities being essentially nickel.
2. An alloy body as in claim 1 which contains about 19 to 21%
chromium.
chromium.
3. An alloy body as in claim l which contains about 6 to 7%
aluminum.
aluminum.
4. An alloy body as in claim 3 which contains essentially no titanium, tantalum, niobium, cobalt, hafnium and rhenium.
5. An alloy body as in claim 4 which contains about 1.5 to about 2.5% molybdenum and about 3 to about 4.5% tungsten.
6. An alloy body as in claim 1 which contains 19 to about 21%
chromium, about 6 to 7% aluminum, about 1.5 to 2.5% molybdenum, about 3 to 8% tungsten, about 0.005% to 0.05% boron, about 0.05 to 0.25% zirconium, up to about 0.1% carbon, up to 1% iron, and up to 0.3% nitrogen.
chromium, about 6 to 7% aluminum, about 1.5 to 2.5% molybdenum, about 3 to 8% tungsten, about 0.005% to 0.05% boron, about 0.05 to 0.25% zirconium, up to about 0.1% carbon, up to 1% iron, and up to 0.3% nitrogen.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US71119985A | 1985-03-13 | 1985-03-13 | |
| US711,199 | 1985-03-13 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CA1255123A true CA1255123A (en) | 1989-06-06 |
Family
ID=24857149
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CA000503724A Expired CA1255123A (en) | 1985-03-13 | 1986-03-11 | Turbine blade superalloy ii |
Country Status (5)
| Country | Link |
|---|---|
| EP (1) | EP0194683B1 (en) |
| JP (1) | JPS61264146A (en) |
| AT (1) | ATE36351T1 (en) |
| CA (1) | CA1255123A (en) |
| DE (1) | DE3660497D1 (en) |
Families Citing this family (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CH671583A5 (en) * | 1986-12-19 | 1989-09-15 | Bbc Brown Boveri & Cie | |
| US4781772A (en) * | 1988-02-22 | 1988-11-01 | Inco Alloys International, Inc. | ODS alloy having intermediate high temperature strength |
| US4877435A (en) * | 1989-02-08 | 1989-10-31 | Inco Alloys International, Inc. | Mechanically alloyed nickel-cobalt-chromium-iron composition of matter and glass fiber method and apparatus for using same |
| CN102162049B (en) * | 2011-04-07 | 2012-12-19 | 上海大学 | Nickel-base alloy material for super-supercritical steam turbine and preparation method thereof |
Family Cites Families (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3926568A (en) * | 1972-10-30 | 1975-12-16 | Int Nickel Co | High strength corrosion resistant nickel-base alloy |
| US3909309A (en) * | 1973-09-11 | 1975-09-30 | Int Nickel Co | Post working of mechanically alloyed products |
| US4386976A (en) * | 1980-06-26 | 1983-06-07 | Inco Research & Development Center, Inc. | Dispersion-strengthened nickel-base alloy |
| US4402746A (en) * | 1982-03-31 | 1983-09-06 | Exxon Research And Engineering Co. | Alumina-yttria mixed oxides in dispersion strengthened high temperature alloys |
| JPS58193335A (en) * | 1982-05-06 | 1983-11-11 | Sumitomo Electric Ind Ltd | Dispersion strengthened type nickel base heat resistant sintered alloy and preparation thereof |
-
1986
- 1986-03-11 CA CA000503724A patent/CA1255123A/en not_active Expired
- 1986-03-13 EP EP86103366A patent/EP0194683B1/en not_active Expired
- 1986-03-13 DE DE8686103366T patent/DE3660497D1/en not_active Expired
- 1986-03-13 JP JP61056020A patent/JPS61264146A/en active Pending
- 1986-03-13 AT AT86103366T patent/ATE36351T1/en not_active IP Right Cessation
Also Published As
| Publication number | Publication date |
|---|---|
| EP0194683B1 (en) | 1988-08-10 |
| JPS61264146A (en) | 1986-11-22 |
| EP0194683A1 (en) | 1986-09-17 |
| DE3660497D1 (en) | 1988-09-15 |
| ATE36351T1 (en) | 1988-08-15 |
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